D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 5400 NUMBER: 84-54-19

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Nacelle - Special Inspection and Rectification of the A-Frame -

ModSum 4-113797

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4003 thru

4055.

Production: The radius increase was incorporated in production using

ModSum 4-113159 at Serial Numbers 4056 and subsequent.

NOTE: The instructions in this service bulletin are only applicable to the systems

and parts installed at the time of delivery on the aircraft or as changed by

Bombardier Aerospace Service Bulletin(s). Before you do this bulletin,

examine all STC or equivalent action changes to make sure this bulletin

can be completed.

Spares Affected:

None
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B. Reason

Problem: A field inspection on one of the aircraft revealed a condition that was

supposed to be corrected during the incorporation of Service Bulletin

84-54-04 (ModSums 4-113279 and 4-113305) was not accomplished. This

condition was an insufficient fillet radius on the A frame base flange.

Solution: This service bulletin provides instructions to do an inspection to check for

the insufficient fillet radius condition & cracks and to repair the condition

if existing.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

- aircraft electrical power is removed

- the nose landing gear lock is engaged

- the main landing gear lock pins are installed thru each main gear and main gear

door mechanism

- an inspection is done to check the A frame base flange for a insufficient fillet radius

and cracks

- if an insufficient fillet radius is found and no cracks are found, aircraft is rectified

using instructions provided in this service bulletin

- if cracks are found, operators are to contact the Help Desk/Action Center for further

instructions

- If sufficient fillet radius is found, aircraft can be returned to service.

- close out.

D. Compliance

Bombardier Inc. recommends incorporation of ModSum 4-113797 at the earliest

opportunity unless otherwise directed by the operator’s airworthiness authority.

A Transport Canada Airworthiness Directive is pending
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E. Approval

The technical content of this service bulletin has been approved under the

authority of the Transport Canada Civil Aviation (TCCA) Design Approval

Organization No: DAO #93-Q-02.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

F. Manpower

PART A - Inspection

It will take an estimated 1.50 man-hours to complete PART A of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure in Part A 1.00

Test / RTS 0.00

Close-Out 0.25

PART B - Rectification

It will take an estimated 2.50 man-hours to complete PART B of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure in Part

B

2.00

Test / RTS 0.00

Close-Out 0.25

For any on-site labor assistance, please speak with a Fleet Services representative

for a quote. The Fleet Services group can be contacted via the Q Series Technical

Help Desk by telephone at 416-375-4000 or email at:

thd.qseries@aero.bombardier.com
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G. Material - Price and Availability

None

H. Tooling - Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

ModSums Manual PSM 1-84-12 ..................................

L. References

The initial issue of this service bulletin was prepared to the engineering drawings

and related data that follows:

DRAWING SHEET REV

8DK4211 1 --

8Z9806 1 --

ModSum 4Q113797 Rev. ‘B’

ModSum 4-113797 Rev. ‘B’

PCA 44090 Revision 0 (for internal reference only)

A Transport Canada Airworthiness Directive is pending

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

None

(1) The following materials are required for the completion of this service bulletin

and may be procured as single items from Bombardier Aerospace Regional

Aircraft or purchased directly from industry sources.
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For alternative equivalent materials, refer to Consumable Products Manual

(CPM) PSM 1-84-18.

Part Number Qty. Per Aircraft Description Alternative

Equivalent

DHMS C4.01

Type 2 (F19)

as required Primer Chromated

Epoxy

see CPM section

07-02

MIL-C-5541

(C1)

as required Chemical Conversion Coatingsee CPM section

07-29A

DHMS C4.04 (F24)

Type 4, Class A

as required Polyurethane

Enamel

see CPM section

07-08

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None

D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set-Up

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING

GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU

DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALLY

RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE

TO THE EQUIPMENT.

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR

MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS

CAN ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN

CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.

(1) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS (refer to AMM TASK’S 24-00-00-861-802 and

24-00-00-910-801).

(2) Make sure that lock pins are installed through each main gear and main gear

door mechanism.
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(3) Make sure the nose gear ground lock is engaged.

(4) Set up the work platforms or ladders as required to gain access to the A frame in

each nacelle. Make sure the work platforms or ladders are electrically grounded.

B. Procedure

Part A - Inspection

(1) On the left and right nacelle inspect the A-Frame aft face, base flange transition

adjacent to the drag strut fitting attachment to determine if a 0.500 + or - 0.03

inch radius is produced in the base flange of the A-Frame 8Z8527, refer to

Figure 6.

NOTE: Rework strap 8Z8534-103 is already manufactured with 0.500 + or - 0.03

inch radius

(2) If 0.500 + or - 0.03 inch radius already exists in base flange of A-Frame 8Z8527

at 2 locations per nacelle, no further work is required. Proceed to Close Out

section of this service bulletin.

(3) If 0.500 + or - 0.03 inch radius does not exist in base flange of A-Frame 8Z8527,

inspect area using eddy current crack detection or fluorescent dye penetrant per

Nondestructive Testing Manual, PSM 1-84-7A.

(4) If there are any cracks, contact Bombardier Help Desk/Action Center for

approved repair instructions.

(5) If there are no cracks, proceed to Part B - Rectification section of this service

bulletin.

Part B - Rectification

CAUTION: PROTECT HYDRAULIC LINES AND HARNESS’S NEAR REWORKED

AREA FROM DAMAGE DURING MATERIAL REMOVAL. (FIGURE 3)

(1) Remove material from A-Frame 8Z8527 as shown in Figure 6, Detail E.

NOTE: Care should be taken to maintain edge distance of 0.32 inch minimum to

hi-lite hole for drag strut, also make sure no damage to shear deck

8Z8536 and rework strap 8Z8534-103.

(2) Finish machined edges per Structural Repair Manual PSM 1-84-3, Chapter

51-14-00.

(3) Clean cut metal edges per Structural Repair Manual PSM 1-84-3, Chapter

51-26-00.
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(4) Improve cut metal edges to achieve a surface finish of 125RMS or finer.

(5) Re-finish reworked areas using the following materials:

(a) Chemical Conversion Coating (C1) per Structural Repair Manual PSM

1-84-3 Task 51-21-10-02-02.

(b) Epoxy Primer (F19) per Structural Repair Manual PSM 1-84-3 Task

51-25-10-02-01.

(c) Polyurethane Enamel (F24) per Structural Repair Manual PSM 1-84-3 Task

51-25-15-02-01.

(6) Re-identify LH Frame as 8Z9806-001 and RH Frame as 8Z9806-002 per Aircraft

Maintenance Manual PSM 1-84-2 Task 20-00-01-910-801.

(7) After identification markings have dried, apply clear coat (no colour) of

Polyurethane Enamel (F24) per Structural Repair Manual PSM 1-84-3 Task

51-25-15-02-01.

C. Close Out

(1) Remove all tools and equipment from the work area.

(2) On incorporation of this ModSum, make an entry that conforms to local

regulatory requirements in the applicable logbook(s). Enter component serial

numbers if applicable. Enter this ModSum number only after complete and

functional incorporation of all work defined in this service bulletin.
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Area of Work

Figure 1
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A-Frame

Figure 2

A-FRAME

8Z8527

REWORK STRAP

8Z8534-103
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Figure 3

A-FRAME

8Z8527

REWORK STRAP

8Z8534-103
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Figure 4

REINFORCEMENT STRAP

8Z8534
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Figure 5
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Figure 6

EXISTING INSUFFICIENT FILLET RADIUS

DETAIL ‘E’ SYMMETRICAL ABOUT CENTER LINE OF EACH NACELLE

MAINTAIN 0.500 + or - 0.03 INCH RADIUS

ON REWORK STRAP 8Z8534-103

A-FRAME

8Z8527

MATERIAL TO BE REMOVED

REWORK STRAP

8Z8534-103

(no rework necessary if 0.500 + or - 0.03 inch

radius exists)

A-FRAME

8Z8527
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This Page Intentionally Blank.

1
Jan 2009

SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION

--- Q SERIES DASH 8 AIRCRAFT

To: CMDB Focal

Facsimile: (1) 416 375 4538

E --mail: cmdb.requests@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

The data that you provide below will help us record the incorporation of this ModSum

and the aircraft effectivity in the maintenance manual.

Operator: Service Bulletin: __________________ Revision: _________

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Aircraft Serial Number: Model Number: Date Bulletin Completed:

Fax this sheet to (1) 416 375 4538 or Email PDF to:

cmdb.requests@aero.bombardier.com
Feb 2009

SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft

Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538

E --mail: syed.rizvi@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

Select appropriate box(es) and add comments or suggestions you would like us to know

that may enhance the quality of our service bulletins.

Service Bulletin: Revision: ModSum:

1. PLANNING INFORMATION

V Effectivity V Reason V Description V Compliance

V Approval V Manpower V Material V Weight and Balance

V Electrical Load V Tooling V References V Publications Affected

2. MATERIAL INFORMATION

V Kit Content V Special Tools/Equipment V Parts to Modify Spares

V Consumables V Disposition of Existing Parts V Other

3. ACCOMPLISHMENT INSTRUCTIONS

V Job Set ---Up V Procedure V Close---Out V Test

V Illustration(s) V Other

4. COMMENTS, REMARKS, SUGGESTIONS

Fax this sheet to (1) 416 375 4538 or Email PDF to:

syed.rizvi@aero.bombardier.com